Fin actuated spin vane control device and method



July 12, 1966 F- w. DIETRICH FIN ACTUATED SPIN VANE CONTROL DEVICE AND METHOD Filed. Sept. 28, 1964 5 Sheets-Sheet l A 4 G ..D d 0 m nL 4 2 2 mm b 0 e I 5 n 4 m 0 2 6 5 .U Q 7 0 V o Q I I m 6 5 Oil F a d 13 G I. 9 Id 5 d C I J M Fl 7 INVENTOR.

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FORREST W. DIETRICI'I ATTORNEY July 12, 1966 F. w. DIETRICH FIN ACTUATED SPIN VANE CONTROL DEVICE AND METHOD 3 Sheets-Sheet 2 Filed Sept. 28, 1964 INVENTOR FORREST W. DIETRICH y M FIG.-9

ATTORNEY United States Patent Office 3,26%,205 Patented July 12, 1966 3,260,205 FIN ACTUATED SPIN VANE CONTROL DEVICE AND METHOD Forrest W. Dietrich, Santa Barbara, Calif., assignor to Aerojet-General Corporation, Azusa, Calif., a corporation of Ohio Filed Sept. 28, 1964, Ser. No. 399,481 11 Claims. (Cl. 102-51) The present invention relates to control means for spin vanes in jet-propelled vehicles such as missiles or projectiles. More specifically, it relates to means for retracting spin vanes from their spin-imparting attitude in response to the unfolding of stabilizer fins on the periphery of a missile.

An object of the invention is to provide spin vane control means for a jet-propelled vehicle which will adjust the attitude of spin vanes and, thus, adjust the degree of spin of such a vehicle, doing so automatically, in response to the movement of stabilizer fins.

A specific object of the invention is to provide pivotally mounted vanes within the nozzle of a jet-propelled vehicle and mechanism connecting said vanes to stabilizer fins about the nozzle so as to trim the vane attitude in response to the unfolding of the fins upon the launching of the vehicle. Thereby the fin movement is automatically made to reduce the angle of attack of the spin vanes and thus reduce the degree of vehicle spin shortly after launch.

Another object of the invention is to provide a Simpler and lighter spin vane adjustment means, thus reducing the weight of the missile and the complexity of the apparatus thereon.

A further object of the invention is to eliminate separate and independent spin vane control equipment and further dispense with the need to jettison such equipment.

Still another object is to provide a novel control linkage between two sets of air foils disposed in two independent fluid media, whereby the movement of one set of foils automatically adjusts the attitude of the other set.

Other objects and many of the attendant advantages of this invention will be readily appreciated and become better understood with reference to the following detailed description and the accompanying drawings.

For purposes of illustrating a preferred embodiment of the invention only, and not by way of limitation, the invention is disclosed herein as applied to an unguided jetpropelled body, that is, an unguided missile. This preferred embodiment is shown in the accompanying drawings, wherein:

FIGURE 1 is a side elevation of a missile in the launch tube and the same missile immediately after launch thereby illustrating .the position of the stabilizer fins before and shortly after launch;

FIGURE 2 is a side elevation of the tail portion of the missile shown in FIGURE 1 embodying the inventive mechanism;

FIGURE 3 is a fragmentary detail of a section through a fin pivot on a larger scale along the lines 33 of the tail portion shown in FIGURE 2;

FIGURE 4 is a fragmentary detail of a section through a vane-controlling cam arm on a larger scale along lines 44 of the tail portion shown in FIGURE 2;

FIGURE 5 is a cross-sectional view looking down upon the base mount for the fins shown in FIGURE 2 taken along lines 5-5 therein, and on a larger scale;

FIGURE 6 is a side elevation of a tail portion of the missile shown in FIGURE 1 similar to that shown in FIGURE 2, but embodying alternative linkage mechanism according to the invention;

FIGURE 7 is an elevational view, greatly enlarged, of the details of one of the inventive cam means shown in FIGURE 6;

FIGURE 8 is a bi-sectional view laid on its side, taken near the top of FIGURE 6 and shown on a greatly enlarged scale; and

FIGURE 9 is a sectional view along lines 9-9 of the showing in FIGURE 8.

It is common in jet-propelled rockets to employ stabilizing fins mounted about the after portion of the rocket motor to maintain the rocket trajectory and prevent unwanted deviations from axial alignment, Such deviations are often caused by misalignment of the rocket motors, weight imbalance, airfoil asymmetry and other sources of aerodynamic instability.

Stabilizer fins are customarily retractably mounted or folded about the rocket fuselage and adapted to be unfolded by centrifugal force, spring action or both, when the missile emerges from its launch tube.

This invention contemplates a new improved more effective means for controlling the attitude of spin vanes within the rocket nozzle employing the opening action of stabilizer fins to change the amount of spin torque imparted by the spin vanes.

Spin vanes are commonly used in missiles or rockets to impart a ballistic spin to the rocket body during its initial trajectory as it is impelled through the launch tube and beyond. Such a spin is important for preventing dispersion or misalignment of the rocket vehicle due to wind thrust and the like. To effect this spin, spin vanes are commonly installed in the rocket nozzle, near the after-portion thereof. It is apparent that such spin vanes must be so mounted as to present an appreciable airfoil surface, i.e., a large angle of attack during launch, so that the gases rushing through the nozzle will impinge upon the relatively large airfoil surface presented and impart a measure of torque to the nozzle body which spins the entire missile. However, it is important to reduce this angle of attack shortly after launch by trimming, i.e., adjusting the attitude of, the spin vanes. Reducing the angle of attack prevents an excessive spin rate which could cause structural failure of the missile itself or spiral instability of the missile in flight. For this reason, spin vanes should be adjustably pivoted within the nozzle.

Generally, it has been necessary to provide motive power to adjust the attitude of spin-vanes and to provide separate, complex control devices to initiate the spin-vane adjustment at the proper time and with the proper degree of spin trim.

The present invention eliminates the need for separate motive and control equipment, thereby saving weight and space. The invention provides a simple effective automatic means for trimming spin vanes shortly after launch. According to the invention this is accomplished by a mechanical linking of the stabilizing fins to the spin vanes so that when the fins unfold, upon emergence from the launch tube, they automatically trim the spin vanes, reducing their angle of attack to a prescribed value, and thus reduce or eliminate spin as desired.

Spin vanes were trimmed in the prior art by the use of special ring supports which were attached to the surface of the missile and had to be jettisoned shortly after launch. Such separable rings were cumbersome and, when jettisoned, became dangerous flying objects. In eliminating the need for such rings, the invention solves a pressing problem in the art.

It will be observed that, according to the preferred embodiments illustrated and described herein, stabilizer fins are made to actuate and control the spin vanes by rotating a cam attached to the fin which in turn rotates a cam ring, and the cam arms to which the spin vane shafts are connected. Thus, when the fins unfold, they will automatically trim the spin vanes and reduce missile spin to a predetermined degree.

Referring now to the drawings wherein like reference characters designate like or corresponding parts throughout the several views, there is shown in FIGURE 1 an unguided missile 40 adapted to employ the instant invention as hereinafter described. Missile 40 is shown at the right of FIGURE 1 in a just-launched attitude, just after it has emerged from the launch tube 46. Missile 4% has an aerodynamically tapered nose 43, and a tail, or exhaust end, 44 from which the propelling gases driving the missile emerge. A set of stabilizer fins 1A, 1B, etc., are shown as disposed about the fuselage of missile 44) adjacent the after portion or tail 44 thereof. Since missile 40 has just been launched from tube 46, fins 1A, 1B, etc., as is customary, will have just opened, or unfolded, from their retracted attitude. This retracted attitude, wherein the fins 1A, 1B, etc., are folded about the periphery of the after fuselage of missile 40 is indicated at 1A, l'B, etc., on the partially phantomed version 40' of the missile lying within partially cut-away tube 46 ready for firing. Of course the number and placement of such sets of fins may vary as known in the art. For instance, a second set of fins may be located adjacent nose 43 and either or both sets be made to control spin vanes according to the invention.

The after-portion of missile 40 is more specifically illustrated in FIGURE 2 wherein the tail section 44 is shown as inverted (tail-end up) and removed from the balance of the missile body 40 to which tail section 44 is joined through an aerodynamically-continuous fairing joint 48. In this view of tail section 44, fins 1A, 1B, 1C and ID are shown as unfolded or opened. The number of fins may vary as long as they are symmetrically disposed about the periphery of missile 40. Fins 1A, 1B, etc., being opened, it will be understood that the elements of missile 40 are in after-launch condition. Thus, it Will also be understood that spin vanes 56A, StlB, etc., rotatably mounted about the interior periphery of nozzle 62 have been trimmed. This trimming, as previously described will decrease or eliminate the spin imparting torque caused when ejected gases from nozzle 62 impinge upon vane surfaces at an oblique angle to the direction of gas ejection. In short, as shown in FIGURE 2 spin vanes 50A, etc., have been rotated so as to be parallel to longitudinal axis 64 of nozzle 62, or nearly so. Fins 1A, etc., will be noted to be mounted rotatably on the periphery of missile 40 on pins 25A, 25B, etc., as shown in greater detail in FIGURE 5 between fairing joint 48 and fin hinge 24A, etc., for each of the fins. As seen more clearly in FIGURES 5 and 9, the fins may thus be caused to unfold about the periphery of missile 4G by being driven rotatably about axes parallel to missile axis 64 by torsion springs 7A, 7B, etc. This unfolding rotation is what actuates the trim rotation of spin vanes 50A, etc. The linkage, whereby the rotation of fins 1A, etc., causes the rotation of vanes 50A, etc., comprises a cam and cam ring arrangement, 51A, 31, 33 as shown in FIGURE 2 or 131, 133, 129A, etc., as shown in FIGURES 5 and 9 and may take the form of other equivalent mechanical linkage known to those skilled in the art simliar to those shown in detail in FIGURES 69. More specifically when a fin, such as 1A in FIGURE 2, unfolds, it rotates a cam 23A adjacent its hinge 24A which is drivingly disposed in a slot (which may be seen in FIGURE 3) in a cam follower, or cam ring 31. Cam 23A rotates ring 31 about nozzle axis 64 (see also FIGURES 3 and 4). As may be seen in FIGURE 4 rotation of cam ring 31 drives cam arms 51A, etc., disposed intermeshingly in cam slots 59A, etc., in cam ring 31. Cam arms 51A, etc., are connected through shafts A, etc., to vanes 50A, etc.

The arrangements whereby the cams 23A, etc., are attached to their associated fins 1A, etc., is better shown by reference to FIGURES 3 and 4. In FIGURE 3, it will be observed, for reference purposes, that tail section 44, fin 1A and vane 50A are positioned relatively the same as in FIGURE 2. Hinges 24A are attached fixedly to tail section 44, for instance, by brackets. Hinges 24A, etc., include a bore in which shafts 26A, etc., are rotatably journalled. On shafts 26A, etc., fins 1A, etc., and earns 23A, etc., are hung. Both cams 23A, etc., and shafts 26A, etc., rotate on hinges 24A, etc. when fins 1A, etc., rotate to unfold. Cams 23A, etc., will drive cam ring 31 rotatably about nozzle axis 64, as a result of being positioned in slots (59A) in cam ring 31.

Reference to FIGURE 4 will more particularly illustratethe cam arrangement whereby cam ring 31 rotates spin vanes 50A, etc. Each of spin vanes 50A, 50B, etc., is mounted rotatably on the inner periphery of the nozzle 62 through shafts 55A, 55B, etc. Cam arms 51A, etc. are fixedly attached to shafts 55A, etc. Rotation of a cam arm 51A on shaft 55A will rotate spin vane 50A attached thereto. Rotation of cam arms 51A, etc., is due to rotation of cam ring 31. Cam arms 51A, etc., are operatively disposed in cam slots 59A, etc. cut into cam ring 31 so that the rotation of cam ring 31 will produce rotation of cam arms 51A, etc., and their associated vanes 50A, etc., synchronously. Therefore, the rotation of cam ring 31 automatically trims spin vanes 50A, 50B, etc., adjusting the angle of attack thereof and reducing the spin of the missile 40. If a plurality of nozzles 62 are employed on a missile, the added nozzles will each likewise be provided with the above described vane-control means according to the invention. Similarly, the above described set of fins 1A, 1B, etc., may be differently located elsewhere along the longitudinal axis of missile 40 or supplemented with other similar sets of fins and such differently located set or sets may be similarly sets of fins and such differently located set or sets may be similarly linked to the spin vanes to control them according to the above described teaching of the invention by equivalent means known to those skilled in the art.

The arrangement whereby fins 1A, etc., are hung upon the fairing joint 48 and caused to unfold will be better understood with reference to FIGURE 2 and FIGURE 5. The periphery of nozzle 62 is here shown as in the center of the missile body 40 and fairing joint 48. Nozzle 62 which surrounds the passageway through which the hot propelling gases are expelled constitutes the throat of the rocket motor. Surrounding nozzle 62 is an annular ring 11 (see FIGURE 5) on which each of a plurality of fin springs 7A, 7B, etc., is fixedly attached by its outer end to an extension 10A, etc., of cam plate 13. Springs 7A, etc., automatically urge fins 1A, etc., into an open or unfolded position when missile 40 clears launch tube 46. Springs 7A, etc., constitute spiral torsion springs arranged to automatically unfold fins 1A, etc. Springs 7A, etc., are wound around spools 9A, etc., shown in dashed line in FIGURE 5. Other fin actuating means such as another form of spring action similar to that of springs 7A, etc., or other drive means may be used by those skilled in the art. The fins may be mounted so that the centrifugal force of the spinning missile will unfold them. The arm portions 21A, etc., of fins 1A, etc., rotate on extensions 15 of fairing joint 48 through axles 25A, etc., rotatably disposed therein. Fins 1A, etc., are guided in slots 22A, etc., by pins 27 projecting from arms 21A, etc., of fins 1A, etc., as stops to limit the outward movement of the unfolding fins. Pins 27A, etc., also ride in groove 22A, etc., turning into extension 28A, etc., of groove 22A, etc., to lock fins 1A in the open position thereof. It is to be noted that extensions 28A, etc., are essentially normal to grooves 22A, etc. As pins 27A, etc., turn the corners of grooves 22A, etc., into extensions 28A, etc., the locking action is effected. The above described or other equivalent means will cause fins 1A, 1B, etc., to automatically unfold during launch once the missile 40 clears its launch tube 46. It should be further noted that the unfolding of fins 1A, 1B, 1C, 1D, takes place simultaneously and the motions of each and the respective positions of each at any instant will be identical with the others.

A further appreciation of the interrelation of spin vanes 50A, etc., and stabilizer fins 1A, etc., together with the linkage connecting the two may be had through examination of FIGURES 6, 7, 8 and 9. These figures also illustrate an alternative linkage embodiment comprising a different equivalent cam arrangement from that shown in FIGURES 1 through 5.

In FIGURE 6, there is shown an emboidment of the invention alternative to that shown in FIGURE 2, where a dilferent linkage means is employed connecting the fins 101A, etc., with the spin vanes 150A, etc. As seen in detail in FIGURE 7, cam arm 151A, etc., bifurcated at one end are fixedly mounted on shafts 155A, etc., at the end 157A, etc., opposite the bifurcated ends of cam arms 151A, etc. Shafts 155A, etc., are rotatable on the periphery of tail section 144. Spin vanes 150A, etc., are fixedly attached to shafts 155A, etc., so that as the bifurcated ends of cam arms 151A, etc., are rotated on shafts 155A, etc., by the movement of cam ring 131 about the axis 164 of nozzle 162 which drives cam arms 151A, shafts 155A, etc., and spin vanes 150A, etc., attached thereto will rotate also. The rotation of arms 151A, etc., trims spin vanes 150A, etc., on which they are mounted through shafts 155A, etc. Cam ring 131 is rotated about the axis 164 of nozzle 162 to drive arms 151A, etc., as shown in FIGURES 1-5. This rotation is caused, as in the embodiment associated with FIGURE 2, by the unfolding of fins 101A, etc., and the concomitant rotation of the cams 123A, etc., associated therewith. Cams 123A, etc., are meshed into cam slots 129A, etc., in cam ring 131. Cam ring 131 is drivingly linked with spin vanes 150A, etc., and their associated cam arms 151A, etc., as above described through pivots 124A, etc., on the periphery of the cam ring 131. Thus, it will be seen that when the unfolding fins 101A, etc., rotate cam ring 131, pivots 124A, etc., will rotate their associated cam arms 151A, etc., and provide the trimming rotation of spin vanes 150A, etc.

A side sectional view of the embodiment shown in FIG- URE 6 is presented in FIGURE 8. By way of orientation, it will be noted that as in FIGURE 6, there is here shown a tail section 144, a nozzle 162 in which are disposed spin vanes, such as 150C and 150F and, linked to the vanes, stabilizer fins such as 101A and IMF. The linkage between the fins 101A, etc., and the spin vanes 150A, etc., is shown, for instance, at fin 101E which, as better shown in FIGURE 9, drives cam ring 131 and pivots 124F, etc., thereon. its associated cam arm 151F, rotatably. Arm 151F is rotated, turning the shafts 155F attached thereto and the spin vane 150F mounted thereon. As before, the degree of rotation of vanes 150F controls the degree of spin imparted to missile 40. This control of spin vane trim is better shown with reference to spin vane 1500. Here the position of vane 1500 indicates that in the fins open position it is aligned so as to present the least amount of spin-imparting surface oblique to path of the propelling gas'es rushing along nozzle axis 164. Likewise, the attitude of vane 150C in the fins closed position indicates that this attitude presents relatively more spin-imparting surface and thus will produce a maximum amount of spinning torque. The attachment of Pivot 124F, in turn, drives 6 spin vane A (for example) to its shaft A is indicated at 158A.

The adjustment in vane attitude is indicated schematically in FIGURE 9, taken along lines 99 of FIG- URE 8.

In FIGURE 9, illustrating the embodiment in FIG- URES 6 and 8 in fragmented sectional fashion, the camfollower arrangement whereby fins 101C, etc., drive the cam ring 131 is more clearly shown. Attached to fin 101C for instance, is a cam portion 123C arranged to engage a cam slot between channels portions 129C along cam ring 131. It can be seen thereby how the unfolding rotation of fins 101C, etc., acts to rotate cam ring 131 about the axis 164 of nozzle 162. This rotational action of fins 101C, etc., is indicated schematically, for instance, where the closed attitude 101'A of the fin 101A is indicated in phantom. The cam arms 151H, etc., are shown in section as disposed operatively in a cam-follower fashion about the pivots 124H, etc., on cam ring 131.

The operation of the invention whereby the unfolding of fins 101A, etc., controls the trim of spin vanes is as follows. The missile 40' is initially disposed in a launching means, such as launch tube 46, with its fins 1'A, 1B, etc., in the folded position retracted closely about the periphery of the missile fuselage presenting a compact silhouette. Upon the actuation of launching forces, such as by initiation of the motor in missile 40' and the expulsion of gases through the tail section 44 thereof, the missile is expelled from the launch tube 46. However, during the expulsion of missile 40' the propelling gases emanating from the tail section 44 traverse the nozzle 62 and the spin vanes which are not shown in the figure but are disposed therein. These vanes being oriented in nozzle 62 with their surfaces oblique to the path of the gases impart a spinning torque to the missile as it begins to emerge from launch tube 46. Upon the complete emergence of missile 40 from tube 46, the fins 1A, 1B, etc., automatically unfold into an open position under the urging of fin springs 7A, etc., as illustrated in FIGURE 5. The unfolding action of fins 1A, 1B, etc., according to the invention initiates the rotation of fin cams 23A, etc., the rotation of cam ring 31, and of cam arms 51A, etc., cooperating therewith. Arms 51A, etc., rotate spin vanes 50A, 50B, etc., into a trim of minimum spin attitude, the fins open attitude shown in FIGURES 6, 8 and 9. The novel result of this is that upon the emergence of missile 40 from its launch tube 46, the opening of fins 1A, etc., reduces spin without any need for independent, auxiliary motive or control means. The operation of the linking cam means in the embodiments shown in FIGURES 6, 7, 8 and 9 is slightly different from that described for FIGURE 2, but is nonetheless effectively similar in its operation.

As will be appreciated by those skilled in the art, the alternative linkage arrangement shown in FIGURES 6-9 is, like the arrangement shown in FIGURES 2-5, is merely illustrative and may be replaced by other equivalent means within the capability of those skilled in this art. It is therefore within the contemplation of the present invention that these other equivalent means can be substituted for the cam means, and may include for example gear segments or cranks and also that the cam ring can be replaced by eequivalent mechanical linkages.

It should be clearly understood that the above described embodiments are merely illustrative of the invention and may be varied within the scope of the claims which are appended hereto to solve similar problems and to employ equivalent elements as known to those skilled in the art. Modifications of the inventive structures described herein and changes in the interrelation of the novel combinations of elements above described will sug gest themselves to those skilled in the art. The embodiments described herein have been selected to illustrate preferred implementations of the invention and are to be understood as not limiting the present invention as defined by the appended claims.

What is claimed is:

1. In a jet-propelled body including a fuselage, a fluid conducting nozzle portion connected with said fuselage and spin-imparting vane means adjustably mounted within said nozzle portion, said vane means being rotatable between a maximum spin attitude and a minimum spin attitude, the combination therewith comprising:

a plurality of structurally integral stabilizer means adjustabiy mounted about the periphery of said nozzle portion so as to assume a first attitude in response to a first condition and a second attitude in response to a second condition, and

vane trim means interconnecting said stabilizer means with said vane means so as to change the attitude of said vane means in response to a change in the attitude of said stabilizer means.

2. The combination recited in claim 1 wherein said first attitude of said stabilizer means is one of retraction closely about the periphery of said fuselage in a pre-launch condition of said body, and said second attitude of said stabilizer means is one of unfolded projection of said stabilizer means relatively normal to the longitudinal axis of said fuselage so as to respond to the fluid stream therealong and maintain said body aligned along said longitudinal axis thereof in response to a post-launch condition of said jet-propelled body.

3. The combination recited in claim 1 wherein said first attitude of said stabilizer means is one of retraction closely about the periphery of said fuselage in a pre-launch condition of said body, and said second attitude of said stabilizer means is one of unfolded projection of said stabilizer means relatively normal to the longitudinal axis of said fuselage so as to respond to the fluid stream therealong and maintain said body aligned along said longitudinal axis thereof in response to a post-launch condition of said jet-propelled body,

and wherein said trim means comprises annular camfollower means arranged to rotate about the longitudinal axis of said nozzle portion,

a plurality of fin-actuated cam means, one of said cam means being connected to each of said stabilizer means in driven relation therewith, said cam means being intermeshed with said cam-follower means so as to cause said cam-follower means to rotate in response to the entry into said second condition by said stabilizer means and a plurality of cam arms, one being connected to each of said vane means in driving relation therewith and further being intermeshed with said cam-follower means so as to cause said vane means to assume said minimum spin attitude in response to the entry into said second condition by said stabilizer means.

4. In a projectile having at least one jet steam of propelling fluid emanating therefrom and at least one nozzle disposed on said projectile to direct said fluid outwardly therefrom, the combination with said projectile comprismg:

a plurality of spin vanes pivotally-mounted within said nozzle,

a plurality of stabilizer fins pivotally mounted about the periphery of said projectile and arranged to rotate between an inactive and an active attitude, and

a trim means mechanically connecting said fins to said vanes so that the rotation of said fins into said active attitude automatically adjusts the attitude of said vanes so as to modify the attack-angle thereof and thereby modify the amount of projectile-spinning torque produced said spin vanes when said jet stream passes therethrough.

5. In a jetapropelled missile including a fuselage, a

motor disposed within said fuselage, at least one nozzle means disposed within the after portion of said fuselage between said motor and the exterior of said after portion to conduct fluid into the medium traversed by said missile, a plurality of spin vanes disposed symmetrically about the inner periphery of said nozzle portion and rotatably mounted thereon, to rotate said missile about axes parallel to the longitudinal axis of said nozzle portion in response to the traverse therethrough of said fluid, and a plurality of aerodynamically-integral stabilizer fin means symmetrically mounted about said fuselage, said fin means being adapted to change from a collapsed to an active condition upon the launching of said missile, the improvement therewith comprising:

mechanical linkage means between said fins and said vanes whereby the entry of said fin means into said active condition automatically causes said vanes to rotate about said axes thereby to modify the degree of missile-spinning force produced by said vanes in response to said fluid passing through said nozzle.

6. A jet propelled vehicle comprising in combination:

a fuselage housing the elements of said vehicle,

at least one nozzle portion disposed along said fuselage and arranged to conduct propelling fluids to the external medium through which said vehicle moves;

a plurality of spin vane means disposed about the inner periphery of said nozzle portion, said vane means being rotatably journalled in said fuselage to pivot about an axis parallel to the longitudinal axis of said nozzle portion;

a plurality of stabilizer means disposed symmetrically about the exterior of said fuselage being rotatably journalled therein so as to pivot about axes parallel to the said longitudinal axis of said nozzle portion;

connector means linking said vane means to said stabilizer means and including a plurality of fin-cam means attached to each of said stabilizer means to rotate therewith, annular cam follower means mounted rotatably about the exterior of said nozzle portion and arranged to mesh with said fin cam means in driven relation therewith so as to be rotated thereby about said axis of said nozzle portion and a plurality of vane cam means disposed adjacent co related cam-slot portions of said cam follower means in driven relation thereto, said vane cam means being affixed to said vane means to rotate in conjunction therewith; and

stabilizer actuating means attached to each of said stabilizer means and arranged to pivot said stabilizer means about said axes in response to a predetermined condition of said vehicle.

7. An automatic spin control system adapted for use in a missile, said missile having an elongated fuselage, said fuselage having a tail portion, said tail portion having at least one nozzle portion thereon, said nozzle portion bernzg arranged to conduct propelling gases outwardly of said tail portion, said missile further including a plurality of stabilizer fins retractably mounted on said fuselage so as to be pivoted between an inactive attitude relatively parallel to a portion of said fuselarge and an active attitude relatively normal to said fuselage, and spin vane means rotatably mounted about the inner periphery of said nozzle so as to rotate between a high spin attitude and a low spin attitude, said control system comprising:

linkage means connecting said fins and said spin vanes so as to rotate said spin vanes and thereby modify the missile spin caused thereby in automatic response to the pivoting of said fins into a different one of said attitudes, said linkage means comprising:

a plurality of fine driven means, one being associated with each of said fins and arranged to be actuated in response to said pivoting of said fins,

a plurality of vane driving means, one being associated with each of said vane means in driving relation thereto, and

connector means linking said fin driven means and said vane driving means in coacting relation.

8. In a ballistically impelled projectile having a fuselage, at least one jet nozzle disposed in the tail portion of said fuselage, at least one set of stabilizing fins disposed symmetrically about a given cross section of said fuselage, said fins being arranged to provide rigid integral airfoils in a first attitude and to be retractable about the periphery of said fuselage in a second attitude when said projectile is in stored condition, and fin actuation means to automatically unfold said fins into said first attitude upon the ejection of said projectile from a launching tube, the combination therewith comprising:

a plurality of cam means, one being attached respectively to each of said fins to be actuated in conjunction therewith;

a rotatable cam ring arranged to intermesh with said cam means in dniven relation therewith, said cam ring further having a plurality of cam slots disposed thereabout;

spin vane means disposed rotatably about the interior of said nozzle, said vane means including shaft means projecting through and rotatively journ-alled in said nozzle and spin vanes afiixed to each of said shaft means; and

cam arm means including cam arms disposed externally of said nozzle and connected to each of said shaft means, said cam arms being intermeshed with one of said cam slots in driven relation therewith whereby the rotation of said fins drives said cam ring rotatably and thereby rotate said cam arms and said spin vanes attached thereto so that movement of said fins will automatically adjust the trim of said spin vanes.

9. In a jet-propelled projectile, the combination comprising:

a fuselage having a nose portion and a tail portion,

said fuselage defining an internal combustion chamber therein,

at least one nozzle portion disposed at said tail portion and connecting said combustion chamber with the medium exterior to said projectile,

spin vane means pivotally mounted in said nozzle portion to effect the spinning of said projectile in response to gases escaping from said combustion chamber impinging on the surface of said spin vanes, said spin vanes being arranged to assume a minimum spin attitude and a maximum spin attitude in which attitudes said spin vanes are aligned along the path and oblique to the path respectively of said escaping gases,

pivots rotatably mounting said vane means in the inner periphery of said nozzle portion for pivotal movement between said respective attitudes,

at least one set of stabilizer fins arranged symmetrically about the exterior of a cross sectional portion of said fuselage,

fin actuation means arranged to adjust said fins from a retracted attitude into an active stabilizing attitude;

and connector means comprising a plurality of first cam means each associated with one of said fins to rotate in conjunction therewith, a plurality of second cam means each associated with one of said spin vanes to rotate in conjunction therewith, and annular cam follower means connecting said first and second cam means to transmit the rotation of said fins to said spin vanes.

10. A jet-propelled vehicle capable of pursuing a predetermined course when traveling through a fluid medium, said vehicle comprising:

an elongated, generally cylindrical fuselage having a nose portion and a tail portion;

a plurality of adjustable fin members normally arranged to project from the exterior of said fuselage having the longitudinal axes thereof parallel with that of said fuselage, said fin members being collapsible into a retracted position substantially coincident with the periphery of said fuselage;

fin expander means operatively engaging said fin members to automatically cause said fins to assume said normal condition;

nozzle means arranged in said tail portion to conduct propelling gases outwardly thereof;

spin vane means disposed about the interior of said nozzle means, being pivotally mounted therein so as to be rotatable into a high spin and a low spin attitude; and

linkage means connecting said vanes and said fin members whereby the entry of said fin members into said normal condition from said retracted condition automatically changes the attitude of said spin vanes.

11. A method of automatically adjusting the attitude of a plurality of first rotatable surfaces disposed within a chamber according to the shift in attitude of a plurality of second rotatable surfaces disposed exterior to said chamber, said method comprising:

attaching a cam member respectively to each of said second surfaces so as to be rotatably driven thereby, connecting a cam arm with each of said first rotatable surfaces in driving relation therewith, disposing annular slotted cam follower means between said pluralities of surfaces to receive all of said cam members and all of said cam arms thereby responding in driven relation to the rotation thereof.

References Cited by the Examiner UNITED STATES PATENTS 2,644,296 7/1953 Sanz et a1 102-50 X BENJAMIN A. BORCHELT, Primary Examiner. V. R. PENDEGRASS, Assistant Examiner. 

1. IN A JET-PROPELLED BODY INCLUDING A FUSELAGE, A FLUID CONDUCTING NOZZLE PORTION CONNECTED WITH SAID FUSELAGE AND SPIN-IMPARTING VANE MEANS ADJUSTABLY MOUNTED WITHIN SAID NOZZLE PORTION, SAID VANE MEANS BEING ROTATABLE BETWEEN A MAXIMUM SPIN ATTITUDE AND A MINIMUM SPIN ATTITUDE, THE COMBINATION THEREWITH COMPRISING: A PLURALITY OF STRUCTURALLY INTEGRAL STABILIZER MEANS ADJUSTABLY MOUNTED ABOUT THE PERIPHERY OF SAID NOZZLE PORTION SO AS TO ASSUME A FIRST ATTITUDE IN RESPONSE TO A FIRST CONDITION AND A SECOND ATTITUDE IN RESPONSE TO A SECOND CONDITION, AND VANE TRIM MEANS INTERCONNECTING SAID STABILISZER MEANS WITH SAID VANE MEANS SO AS TO CHANGE THE ATTITUDE OF SAID VANE MEANS IN RESPONSE TO A CHANGE IN THE ATTITUDE OF SAID STABILIZER MEANS. 